Abstract: A joint for deploying and locking a solar panel or a reflector has a fork which is pivotable through 180.degree. about a common pivot axis with a fixed bearing support. A disk mounted on the fixed bearing support has a sliding curve that terminates in a groove. A latching fork mounted rotatably on pivotable fork has a latching bolt and sliding roller which runs on the sliding curve when the pivotable fork deploys, and together with a latching bolt, engages the groove. A leg spring engages the latching bolt. The sliding curve has a shape such that during the first half of a deployment angle of the fork that is pivoted by the force of a coil spring, a decreasing portion of the coil spring moment is stored in leg spring. In the second half of the deployment angle, a moment 16 stored in leg spring 9 is again added increasingly to the movement, so that during deployment, an approximately constant corrected deployment moment is provided.

Abstract: The sun search method for a satellite stabilized in three axes according to the invention uses a sun sensor device with a visual field possibly containing gaps, and a rotational speed gyro which measures in a measuring axis that is oriented arbitrarily. A regulating law with the form .tau.=-kGG.sup.T .omega. is used (.tau.=regulating torque, k=amplification factor, G=directional vector of measuring axis of rotational speed gyro, .omega.=rotational speed vector of the satellite). A rotational wheel momentum H which is not parallel to the measuring axis, is generated with the aid of an additional flywheel device.

Abstract: A guided missile with ram jet drive, with an engine occupying the airframe cross section, with two outer air intakes in the lower area of the airframe, which lead to the tail with wake shafts, with a tail plane including four separately pivotable vanes in the form of a diagonal cross. A rigid wing arrangement is provided in or in front of the center of the missile. One drive unit with linear movement is provided for each vane. Two of the drive units are arranged longitudinally offset in the longitudinal and circumferential directions of the guided missile in each wake shaft. A kinematic connection from the drive unit to the lower vane is formed by a coupling rod each with joints at both ends. A kinematic connection from the drive unit to the upper vane is formed by a pivotable double lever each and a coupling rod with ball joints at both ends.

Abstract: A controlled, saturated high frequency power amplifier, which can be used especially as a transmitting amplifier in a T/R module for a phase-controlled (radar) antenna for the X-band (8 GHz to 12 GHz). In this case, a portion of the HF output signal is utilized to generate a control signal, with which the output power is controlled nearly without loss via at least one gate connection for the HF power amplifier components, preferably, field effect transistors, that are components of the power amplifier. The power amplifier thus has a high degree of transmitting effectiveness, even with a pulsed transmitting operation.

Abstract: A wall structure for fuel-cooled engine walls, with a cooling structure having an inner wall to which hot gas is admitted; an outer wall located at a spaced location therefrom; as well as a plurality of webs, which connect the two walls and divide the intermediate space between the walls into cooling channels (19), and with a support structure in the form of at least one stable outer jacket. The cooling structure is slotted from the outside in the area of each web, wherein the slots (22) pass through the outer walls and the centers of the webs into the area of the inner wall. The support structure is designed as an elastically nonrigid support structure at least in the area joining the cooling structure and/or is located at a spaced location from the cooling structure.

Abstract: The invention provides a method for continuous acquisition, identification, and attack of helicopters operating with concealment, using a missile with an integrated target search head computer control. The visual field of the search head is adapted optimally in both the search phase and in the target tracking phase. During the search phase, the missile travels a flight path roughly parallel to the surface of the ground, and the axis of the line of sight is directed diagonally downward at a suitable angle. During a target tracking, the line of sight runs collinearly with the missile axis. The natural radiation of the helicopter modulated by the rotor blade movement is used for target recognition.

Abstract: A triaxially stabilized earth oriented satellite is provided with an attitude control system. The attitude control system contains a controller, final control elements for generating control torques around each of three axes of a system of coordinates (principle axes x, y, z) fixed relative to the satellite. Additionally, the attitude control system comprises, as measuring transducers, exclusively a direction vector measurement device, like a magnetometer or star sensor, a sun sensor array and an earth sensor. The process of the invention makes use of the apparatus as noted above and includes the steps of:A. determining an estimate for the rotating velocity of the satellite from a direction vector measurement;B. searching for the sun, depending on the size of the field of view of the sensor, by one or two search rotations at right angles to the optical axis;C. adjusting the direction of the sun relative to the optical axis; andD. adjusting the direction vector measurement to a reference direction S.sub.

Abstract: A releasing device for rocket fuel lines, arranged between a tank outlet and a shutoff valve, which releases the flow path at a defined, tank-side overpressure, with a piston-like bursting element. A disk is provided with a predetermined breaking point and with a clamping flange, as well as a guide rod that is rigidly attached to the disk, and a catching basket that is permeable to flow and fixes the disk in a positive-locking manner after rupture and axial movement.

Abstract: An electrical conductor for a spacecraft solar generator with at least one solar module, wherein the electrical conductor is made of an alloy containing gold and traces of at least one of silver, palladium or copper and which can be used as a solar cell connector. The electrical conductor advantageously cannot be oxidized by atomic oxygen, has a high hardness and elasticity and can thus withstand high thermal stresses. Furthermore, the electrical conductor can be processed by resistance welding without damaging the cell.

Abstract: A weapons system/device is provided for a dazzling laser with directed laser radiation with a laser operating in the visible range. This is integrated in a rifle-like carrier with an aiming device, range finder, and a portable power supply unit. The laser is adjustable in terms of beam divergence, energy to be emitted, and irradiation time. A control computer is provided for entering target reconnaissance parameters, as well as measuring instruments for determining these parameters with respect to a target subject and the environment. The controls/instrumentation are associated with the laser, wherein the control computer calculates the laser parameters (beam divergence, single pulse or pulse train, pulse energy and pulse count of the pulsed laser) necessary for the reversible dazzling of the eye on the basis of the target reconnaissance parameters entered, and it automatically presets and regulates the resulting laser power and the exposure time of the continuous laser.

Abstract: An arrangement of outlet devices for releasing into the atmosphere cryogenic, combustible exhaust vapors in the near-surface, flow-swept, outer area of aircraft, land vehicles and watercraft. The arrangement provides at least one outlet device on the top side of a component at the top end of a pylon, which is favorable in terms of flow, in the free, undisturbed air flow. Each outlet device is arranged, designed and oriented such that the exhaust vapor is released in at least one directed jet oriented to the rear or to the rear and upward, with or without a lateral component, and is kept away from air inlets, hot exhaust gas jets and other sources of ignition, as well as from surfaces of components.

Abstract: The invention provides a device for unfolding solar panels 2, 3 for a spacecraft, which solar panels are connected with one another by an articulated axle 4, which in turn is connected with actuating devices for unfolding the panels by way of a tension device gearing provided with cable pulleys 11. An uncoupling mechanism, operative after unfolding of one panel 3, permits the articulated axle 4 to be separated from the tension device gearing. Upon swivelling of the unfolded panel 3 into an unfolded position, a pin 8, which is arranged in parallel to the articulated axle 4 engages in circumferentially extending grooves 12 and 12a. In this manner, the swivelled panel 3 can be guided to follow the solar altitude.

Abstract: A landing process and arrangement for payloads from aerospace missions with a steerable gliding body deployable at high altitudes for accurately returning the payload to the earth surface wherein delicate and stressable elements of the payload are to be recovered. The gliding body is filled with a light gas during its deployment, and the aerostatic lift must be lower than the weight of the landing unit. The payload is divided into a body with delicate elements and a body with stressable elements, wherein the body with the stressable elements is suspended on a pulling element at a spaced location under the other body. After the lower body has come into contact with the ground, the upper body is maintained suspended aerostatically.

Abstract: A directional coupler that can be produced entirely in integrated technology (MIC or MMIC), particularly for the X-band. The directional coupler can be designed for a high coupling attenuation (>30 dB) and a high directivity (>30 dB) with a large relative bandwidth (approximately 20%). This is achieved with a stepped arrangement comprising a plurality of .lambda./4 waveguide sections and coupling capacitors disposed between the respective paths of the coupler.

Abstract: In order to produce lightweight mirror structures or other reflecting components, preformed silicon elements of sufficient wall thickness are applied to a CFC or CMC substrate structure with the dimensions of the component to be produced, at a temperature in the range 1300.degree. C. and 1600.degree. C. either in vacuum or in a protective atmosphere. In this way a mirror structure or reflector is formed directly. It is possible to work at temperatures in the range of 300.degree. C. to 600.degree. C. when the silicon is applied in the form of a preform such as a wafer, which is joined to the substrate by way of a zone of a melt eutectic incorporating a nonferrous metal, which is preferably gold. The surfaces are subsequently coated.

Abstract: A projectile, particularly for nonlethal active components. The projectile has a disintegratable shell with pyrotechnic means. The projectile has two or more shell layers made of explosive foil, each alternating with another shell layer made of supportive foil material, between a radially outer shell layer made of supportive foil material and a radially inner protective shell. The different layers made of explosive foil can be ignited sequentially when viewed radially from the outside to the inside.

Abstract: The present invention pertains to a device with nonlethal interference active bodies for combating aircraft, which violate or do not heed flight bans, etc., and can be forced to land due to vibrations and interferences in the air current on the aerodynamic surfaces. A series of embodiments are described and depicted in the figures of the drawing.

Abstract: A projective device especially useful against hollow charge projectiles is formed of a plurality of spaced apart layers inclined obliquely to the main firing direction of the projectiles. A centrally located combination layer consists of two disrupter layers sandwiching a reaction or explosive layer. On either side of the combination layer is a retardation layer. A movably displaceable layer is located on the opposite of one retardation layer from the combination layer and forms the outside surface of the device, while an immovable layer is on the opposite side of the other retardation layer from the combination layer and forms the inside surface of the device. When a hollow charge projectile impacts against the device, the hollow charge spike generated by the projectile is disrupted on its path through the device so that the effectiveness of the spike is seriously impeded.

Abstract: A process for locating mobile stations in a cellular mobile radio network with several spatially distributed fixed base stations associated each to several cells and several mobile stations. The network has storage devices which contain information about the identify of the mobile stations and about the cells in which the individual mobile stations were last signaled. In order to locate a mobile station in as flexible as possible a manner, but also if required as precisely as possible, the information in the storage devices is used for approximately locating the searched-for mobile station and at least one direction finding is carried out in order to more precisely locate the mobile station. A cellular mobile radio network for carrying out this process is characterized in that the individual stations are each in communication with a direction finder and that the mobile radio network has a locating central office in communication with all direction finders.

Abstract: A process is disclosed for determining the position and/or the displacement in time (trace) of a (radar) target surface by a radar installation. A predeterminable number M of the largest echo amplitudes is first determined for the target surface, as well as the corresponding resolution cells (distance and azimuth coordinates). By averaging the distance and azimuth coordinates of the selected resolution cells, coordinates are determined for a reference point that is stable in space in relation to the target surface. This reference point is used for locating and/or tracing objects in particular ships.